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公开(公告)号：US20200052552A1
公开(公告)日：2020-02-13
申请号：US16516796
申请日：2019-07-19
Applicant: ROLLS-ROYCE plc
Inventor： Stephen M. HUSBAND , Gian INCERPI
Abstract: An engine system comprises first and second electrical generators coupled to lower and higher pressure (LP, HP) shafts respectively of a gas turbine engine. A controller is arranged to receive a signal corresponding to a total electrical power demand P1 and to output control signals to the electrical generators in response thereto such that the first and second electrical generators output electrical powers (1−y)P1 and yP1 respectively when P1≤Pm1, where 0.5
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公开(公告)号：US20230160344A1
公开(公告)日：2023-05-25
申请号：US18158683
申请日：2023-01-24
Applicant: ROLLS-ROYCE plc
Inventor： Graham P. BRUCE , Stephen M. HUSBAND , David F. BROOKES
CPC classification number: F02C7/275 , F01D15/10 , F02C3/113 , F02C7/32 , H02K7/1823
Abstract: An electrical system having a first dual-wound rotary electric machine mechanically coupled with a first gas turbine spool and having a first three-phase sub-machine and a second three-phase submachine; a second dual-wound rotary electric machine mechanically coupled with a second gas turbine spool and having a third three-phase sub-machine and a fourth three-phase submachine; and a set of N = 4 bidirectional converter circuits for conversion of alternating current (ac) to and from direct current (dc), each of which has an associated index n = (1, ... , N), and for all n, the ac side of the nth bidirectional converter circuit is connected with the nth three-phase sub-machine. The dc side of the first converter circuit is connected with the dc side of the third converter circuit, and the dc side of the second converter circuit is connected with the dc side of the fourth converter circuit.
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公开(公告)号：US20210071583A1
公开(公告)日：2021-03-11
申请号：US17002044
申请日：2020-08-25
Applicant: ROLLS-ROYCE plc
Inventor： Graham P. BRUCE , Stephen M. HUSBAND , David F. BROOKES
Abstract: Electrical systems for connecting rotary electric machines with gas turbine spools are provided. One such electrical system comprises: a first dual-wound rotary electric machine mechanically coupled with a first gas turbine spool and comprising a first three-phase sub-machine and a second three-phase submachine; a second dual-wound rotary electric machine mechanically coupled with a second gas turbine spool and comprising a third three-phase sub-machine and a fourth three-phase submachine; and a set of N=4 bidirectional converter circuits for conversion of alternating current (ac) to and from direct current (dc), each of which has an associated index n=(1, . . . , N), and for all n, the ac side of the nth bidirectional converter circuit is connected with the nth three-phase sub-machine. The dc side of the first converter circuit is connected with the dc side of the third converter circuit, and the dc side of the second converter circuit is connected with the dc side of the fourth converter circuit.
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公开(公告)号：US20190271267A1
公开(公告)日：2019-09-05
申请号：US16275861
申请日：2019-02-14
Applicant: ROLLS-ROYCE plc
Inventor： Stephen M. HUSBAND , Lixin REN
Abstract: A heat exchanger for a ducted fan gas turbine engine has a low temperature side and plural high temperature sides. The heat exchanger is configured such that heat is extracted from respective engine fluids flowing through the high temperature sides and is received by a portion of a bypass airflow of the engine which, on passing through the fan duct, is diverted through the low temperature side of the heat exchanger thereby cooling the engine fluids.
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Patent Agency Ranking
公开(公告)号：US20230184163A1
公开(公告)日：2023-06-15
申请号：US17940748
申请日：2022-09-08
Applicant: ROLLS-ROYCE plc
Inventor： Paul R. DAVIES , Gareth E. MOORE , Stephen M. HUSBAND , David R. TRAINER , David P. SCOTHERN , Luke GEORGE
CPC classification number: F02C6/20 , F02C7/32 , F02C7/36 , F05D2220/323 , F05D2220/70
Abstract: A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate a maximum electrical power PEM1 (W), and the gas turbine engine is configured to generate a maximum shaft power PSHAFT (W); and a ratio R of:
R
=
(
Maximum
Electrical
Power
Generated
=
P
E
M
1
)
(
Maximum
Shaft
Power
=
P
S
H
A
F
T
)
is in a range of between 0.005 and 0.020.-
公开(公告)号：US20230167786A1
公开(公告)日：2023-06-01
申请号：US17940480
申请日：2022-09-08
Applicant: ROLLS-ROYCE plc
Inventor： Paul R. DAVIES , Gareth E. MOORE , Stephen M. HUSBAND , David R. TRAINER , David P. SCOTHERN , Luke GEORGE
CPC classification number: F02K3/06 , F01D15/10 , F02C7/141 , F05D2220/36 , F05D2220/323 , F05D2260/213 , F05D2260/606
Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine. The core engine includes an intermediate-pressure compressor, high-pressure compressor, and high and low-pressure turbines. The high-pressure compressor rotationally connects to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor rotationally connects to the low-pressure turbine by a second shaft. The heat exchanger module fluidly communicates with the core engine by an inlet duct. The heat exchanger module includes a central hub and multiple heat transfer elements extending radially from the hub and spaced in a circumferential array, for heat energy transfer from a first fluid within the elements to an inlet airflow passing over a surface of the elements prior to airflow entry into an inlet to the core engine. The gas turbine engine further includes a first electric machine rotationally connected to the first shaft, and positioned downstream of the heat exchanger module.
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公开(公告)号：US20210070463A1
公开(公告)日：2021-03-11
申请号：US17001990
申请日：2020-08-25
Applicant: ROLLS-ROYCE plc
Inventor： Stephen M. HUSBAND , Jeffrey HOBDAY , Graham P. BRUCE , David F. BROOKES
Abstract: Electrical systems for connecting rotary electric machines with gas turbine spools are provided. One such electrical system comprises: a first rotary electric machine mechanically coupled with a first gas turbine spool and a second rotary electric machine mechanically coupled with a second gas turbine spool, each said electric machine having an identical even number N≥4 of phases, each phase having a respective index n=(1, . . . , N), and each phase comprising an identical number P≥1 of coils wound in a P-plex configuration in which adjacent phases are radially separated by 2π/NP mechanical radians; a first set of N bidirectional converter circuits for conversion of alternating current (ac) to and from direct current (dc), each converter circuit having a respective index n and being connected with the P coils in the nth phase of the first rotary electric machine; a second set of N bidirectional converter circuits for conversion of ac to and from dc, each converter circuit having a respective index n and being connected with the P coils in the nth phase of the second rotary electric machine; and a number 1≤R≤N/2 of dc outputs for connection with an R-channel electrical network. Each dc output has respective index r=(1, . . . , R); wherein for all r, the rth dc output is connected with the dc side of the nth converter circuits in both the first set and second set, for which n (mod R)≡r is satisfied.
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18.发明申请公开(公告)号：US20200173367A1
公开(公告)日：2020-06-04
申请号：US16679568
申请日：2019-11-11
Applicant: ROLLS-ROYCE plc
Inventor： Stephen M. HUSBAND , Ahmed M.Y. RAZAK , Paul R. MILLER
Abstract: A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: increasing an angular velocity of a low pressure compressor; determining if an exit pressure of the low pressure compressor is equal to or greater than a first threshold pressure; in response to determining that the exit pressure of the low pressure compressor is equal to or greater than the first threshold pressure, controlling rotation of the low pressure compressor using a first electrical machine and controlling rotation of a high pressure compressor using a second electrical machine, to increase angular velocity of the high pressure compressor; determining if an exit pressure of the high pressure compressor is equal to or greater than a second threshold pressure.
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公开(公告)号：US20200025066A1
公开(公告)日：2020-01-23
申请号：US16269810
申请日：2019-02-07
Applicant: ROLLS-ROYCE plc
Inventor： Stephen M. HUSBAND , Ahmed MY RAZAK
IPC: F02C3/04
Abstract: Apparatus for a gas turbine engine, the apparatus comprising: a low pressure compressor; a high pressure compressor; a first electrical machine configured to provide torque to the low pressure compressor; a second electrical machine configured to receive torque from the high pressure compressor; and wherein the high pressure compressor does not comprise a sub-idle bleed valve.
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